Rocket apparatus



Marh12,1946. 6 R. H. GODDARD 2,396,566

ROCKET APPARATUS Filed May l5. 1959 4 Sheets-Sheet l March 12, 1946. l R H, GODDARD 2,396,566

ROCKET APPARATUS Filed May l5, 1939 4 Sheets-Sheet March 12, 1946. R. H. GODDARD ROCKET APPARATUS Filed May 1s, 1939 4 Sheets-Sheet 3 Y @www March 12, 1946.

R. H. GODDARD 2,396,566

ROCKET APPARATUS 4 Sheets-Sheet 4 Filed May l5, 1959 Patented Mayr. 12, 194e ROCKET APPARATUS Robert H. Goddard, Roswell, N. Mex., assigner of one-haii' to The Daniel and Florence Guggenheim Foundation, New Yorlr, N. Y., a corporation of New York Application May 15, 1939, Serial No. 273.600 12 Claims. (Cl. 102-345) This invention relates to rocket apparatus adapted for purposes of high altitude research and propelled by ignition of successive charges of detonating or explosive material.

One important object o my invention is to provide a rocket in which said detonating or explosive material is ignited in a relatively unconiined condition, whereby excessive pressure and over-heating in the rocketv are avoided.

A further object' of my invention is to provide an improved type of nozzle having a reflecting surface so designed that gases approaching said surface from points within the nozzle will be reflected axially rearward of the apparatus and will thus exert a maximum propelling force thereon.

I also provide an improved form of cartridge, improved means for feeding successive cartridges to ring position, and novel means for successively igniting the 4cartridges thus positioned.

Briefly described, my improvedv rocket apparatus contemplatesl successive presentation and ignition of elongated detonating or explosive cartridges in axial but unconned position within a nozzle having its inner end formed substantially as a 90 cone. The nozzle thus has the property of reflecting al1 of the explosion gases along rearward paths substantially parallel to the axis of the nozzle. As the explosive force of the gas vis thus reflected rather than resisted, excessive pressure and strain are avoided and also objectionable heating of the reflecting surfaces.

My invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.

A preferred form of the invention is shown' in the drawings, in which:

1 Fig. lY is'a sectional side elevation of my improved rocket apparatus and with certain duplicated parts omitted for clearness;

Fig. 2 is an enlarged sectional view of certain parts shown in Fig. 1;

Fig. 3 is a detail view of a float valve to be described;

Fig. 4 is a diagrammatic view showing the method of nesting the cartridges;

Fig. 5 is a sectionalside-elevaton of certain recoil mechanism;

Fig. 6 is' a detail side view of a hinged feeding arm to be described;

Fig. 7 is a detail View of a star wheel and holding spring plate to be described;

Fig. 8 is a sectional plan view of certain parts shown in Fig. 2; I

Fig. 9 is a perspective view of an escape device;

Fig. 10 is a side elevation of mechanism for advancing a cartridge to tiring postion;

Fig. 11 is a plan view of certain parts shown Fig. 10;

Fig. 12 is a side elevation of a part of the cartridge-feeding mechanism;

Fig. 13 is a perspective view of parts of a cartridge-releasing device, also shown in Fig. 12;

Fig. 14 is a perspective view of one of the side plates shown in Fig. 12;

Fig. 15 is a perspective view of another part of the linkage shown in Fig. 12;

Fig. 16 is a perspective view transfer rod;

Fig. 17 is an exploded view of a door and spring for a cartridge-*soaking compartment;

Fig. 18 is a detail sectional elevation of a cartridge-firing device to be described;

Fig, 19 is a view similar to Fig. 3 but showing the oat valve in an opened position;

Fig. 20 is a perspective view of the cartridgesoaking and feeding mechanism;

Fig. 21 is a wiring diagram for the load-dumpof a cartridgeing devices;

Fig. 22 is a partial sectional front elevation similar to Fig. 1 but on an enlarged scale Iand showing additional parts in their operative relation to the vertically reciprocating reflector and just prior to ignition of the cartridge, and with certain duplicated parts omitted for clearness,

Fig. 23 is a view similar to Fig. 22 but showing the parts'with the reflector raised and the cartridge carrier advanced to present a fresh cartridge in ring position and also with certain duplicated parts omitted, and

Fig. 24 is a detail side elevation of a portion of the lower end of the xed inner casing.

Referring to Figs. 1 and 2, my improved rocket apparatus comprises a iixed outer casing 20, a fixed inner casing 2i, and a reilector 22 within which explosion or detonation of successive cartridges C takes place.

The reflector 22 is mounted at the lower end of a tube 23 which is slidable upward in an outer tube 26 (Fig. 5). A coil spring 25 is mounted `between the upper end of the outer tube 24 and a flange 26 within the tube 23 and acts to move the reflector yieldingly to the normal rearward `or lower position shown in full lines in Fig. 1.

. Aplurality of pinions i in its upper portion and a parabolic surface in its lower portion.

With this construction, gases produced by detonation or explosion within the upper part of the reector 22 will travel radially outward until they engage the conical surface of the reflector, whereupon they will be reflected rearwardly and substantially parallel to the axis of the apparatus and will thus exert their forces of explosion and expansion to the greatest advantage' and directly in the line of night. Furthermore, as the cartridge C is at no point closely confined within the reflector, no excessive pressures are developed and overheating of the reflecting surface is also avoided.

The cartridges C vmay be of any suitable type but as shown herein they are preferably formed of a solid but porous material, such as carbon, which is thoroughly soaked in an oxidizing liquid, such as liquid oxygen, before b eing placed in the reflector 22 for explosion or detonation. This combination' of solid and liquid elements is particularly effective, as the required proportions and intimate mixture of elements is veasily attained and the cartridges are non=explosive in storage and until immersed.

For the storage and subsequent immersion of cartridges of the type described, I provide the rocket casing with a partition 30 (Figs. 1 and 22) which provides an upper or tank portion 32 to contain an oxidizing liquid and a lower or magazine portion 33 in which a large number of cartridges may be stored. utilize the magazine space to the greatest advantage, the cartridges C are preferably of the hexagonal cross section yindicated in Fig. 4 and are closely nested in the magazine portion 33 of the rocket. A thin perforated casing mayl be provided for each cartridge, if desired, as shown in my prior-Patent`No- 1,341,053. The means for feeding the cartridges C from the different storage compartments in the magazine forms no f part of my present invention but may be as shown and described in my prior Patent No. 1,103,503.

An annular trough d0 (Figs. 1 and 10) is provided near the rear or lower end of the rocket, which trough receives oxidizing liquid from the tank 32 through a supply pipe di. This pipe is closedv at its lower end by a valve d2 (Fig. 3) raised by a iioat d3 when the trough d0 contains a sufficientl supply of liquid.

A small vent opening dit (Fig. 1) in the upper part of the magazine 33 permits gasesevaporating from the liquid in the trough 401to pass upward through the magazine, thus pre-cooling the cartridges before they are delivered to the trough 40 for immersion.

The tube 2d is mounted on a disc 25 (Figs. 1 andv 2) and is reenforced by a casing member d6 nxed at its upper end to the tube 25 and at its lower end to the disc 455. The disc is engaged on its upper surface -by a plurality of rollers dl mounted on the inner surface of the fixed inner casing 2i-and the disc is thus' held from upward movement in the casing.

A circular rack (Figs. 1 and 2) is mounted in the fixed inner casing 2i and is engaged by a (Fig. 8) mounted on short shafts 52 rotatable in bearings 53 secured to the under face of the disc d5. The pinions 5I also engage rack teeth 5d formed on the lower edge of the disc d5. The circular rack 50 and pinions 5| thus constute supporting means for the disc 45 `and thel parts carried thereby, and

In order to also provide means for intermittently rotating .the disc 55, as will now be described.

One of the shafts 52 is provided with a star wheel (Figs. 7 and 8) which is engaged by the 5 pivoted outer end 5] of an arm 58 (Fig. 6) which is mounted on the inner tube 23 and travels vertically in a slot (Fig. 2) in the outer tube 24. The arm 58 and slot 60 thus prevent relative angular movement between the tubes 23 and 24, while permitting free relative axial movement.

'.'I'he'arm 51 (Fig. 6) is'free to swing downward on engagement of the star wheel 53 as the tube 23moves upward, but is unyielding in the opposite direction, so that it engages and positively advances the star whe`el 55eme space each time the tube 23 and reflector 22 move downward or rearward. A spring 59, (Fig. 6) holds the arm 51 yieldingly upward and a spring 6i (Fig. 7) yieldingly engages the star wheel 56 and prevents accidental rotation thereof. The upper end of the tube 24 abuts the under side of the fixed inner casing 2l and may be centered thereon b a bearing ring 62 (Fig. 5).

Each time that a cartridge C is exploded within the reflector-22, the reflector is forced upward or forward by recoil action against the spring 25, and on its return downward movement the arm 5l (Fig. 8) actuates the star vWheel 56 and pinion 5| to angularly advance the gear 50, disc 45, casing member 46, tubes 24 and 23 and reflector 22 one space relative to the fixed outer casing 20 and fixed inner casing 2|, for cartridge-feeding purposes to be described.

l A plurality of magazine tubes or compartments 85 10 (Figs. 11 and 20) are provided between the fixed casing members 20 and 2i, these compartments being spaced apart sufliciently to accommodate certain devices for` successively presenting the cartridges in firing position. 40 The lowermost cartridge from each compart ment 10 is immersed in the liquid in thetrough 60 and remains so immersed during an entire revolution of the disc 45 and parts carried thereby. Each cartridge is then moved radially to an inner compartmenty 10B by selective operating means and is then lifted above the compartment 10 to the position indicatedv in dotted lines in Fig. 10, from which position it is advanced-to axial alignment with the reector 22 and the tubes 23 and 24.

Successive cartridges are moved inward by levers 'Il (Fig. 12) each having a pair of hooks 12. adapted to extend behind a cartridge C and to -move the cartridge to its compartment llia when the lever 'Il is swung to the right'as viewed in Fig. 12. The means for thus swinging the' lever will be hereinafter described. l

When in the compartment 10, the lower end of the cartridge rests on a plate 14 (Figs. 10 and 60 16) secured to the lower end of a thin rod 'i5 having an offset upper end or hook i6 and normally held downward by a spring 11.

The upper ends I6 of the rods 15 are successively engaged by a lug (Fig. 1l) on the outer edge of the reflector 22 as the reflector moves up 3l (Figs. 10 and 1'?) o'verlies each inner compartliquid oxygen and also prevents loss of liquid by tilting or jarring of the apparatus. I

The offset end or hook 16 of the rod 15 slips ofi of the lug 80, due to the resilience of the rod, when the plate 1d reaches its extreme upper position and engages the upper end of the compartment 108. The spring 11 then returns the rod 'l5 and plate 14 to the position shown in Fig. 10.

When the cartridge is moved to its raised position, it is received in a carrier 90 (Fig. 12) which is open at its front side, except for a removable hook 9|, Each carrier 90 is mounted on `a plurality of side plates 92, pvotally supported on the fixed outer casing 2|) Vand extending inward through a slot 2in (Fig. 24) in the lower part of the fixed inner casing 2| and constituting a lazytongs Vstructure of the usual type. spring 93 acts to normally hold each carrier in withdrawn or outer position.

Each carrier is operated by engagement of the lug 8|) on the reilector 22 with a hooi: 25 at the upper end of a spring 96 normally coiled on a rod 91 having its lower end pivoteci at @d on a plate (Figs. 12 and 15).

The Plate 99 is pivoted on the stud lub which connect/s the pivoted ends ol' one pair of side plates 92, and is provided with a spring arm lui (Fig. l) having an offset end |02 projecting into an opening |03 in one of the arms Q2. The spring il@ is thus yieldingly connected to actuate the lazytongs structure and advance the carrier @El to the axial position indicated in full lines in Fig. 1l. such movement being limited by stops ldd on certain plates 92 which engage abutting surfaces on other plates 92 when the carrier reaches axial position.

The plate 99 also has an odset arm tu@ (Figs. 12 and 15) which slips into the l-shaped opening between two of the arms 92 as the carrier do reaches axial position. A rod |01 is pivoted to the outer end of thearm 99, and the upper end of the rod is guided at |02 to engage the hook Si@ and remove the hook from holding positionwhen the rod is forced upward.

The parts 9U to |01 are duplicated fenn each of the inner compartment-s lill arranged annular-ly within the casing 2li. The reector 22, however, has only a single lug Bil which will engage only one of the hooks 95 in any given position and which is intermittently advanced to successively engage the hooks.

By such engagement, the corresponding car tridge carrier 90 is advanced to axial position, where it is momentarily held stationary by the action ofthe lug |06 (Figs. 12 and l5). The refiector 22 continues to move upward and increasingly tensions the spring 96. `When the spring sii overcomes the vspring |0|, it turns the arm 92 anti-clockwise on its -pivot illu, thus moving the rod |01 upward to displace the catch 9i clearly shown in Fig. 20.

.As the reflector 22 thereafter moves downward, the spring 93 withdraws the carrier Sulbut the cartridge C remains momentarily in its advanced position by reason of its own inertia. The reilector and cartridge then move downward to the position shown in Fig. 22, and on slight further downward movement the cartridge C is ignited. Although the cartridge remains unsupported during the final downward movement of the reector the time interval is so short that no substantial displacement of the cartridge takes place.

The feeding arm 1| (Fig. 12) oi the next compartment 10a is mounted in -lxed relation to one of the side plates 92 in such manner that it moves to the right in Fig. 12 as the carrier 30 is advanced to axial position. The arm 1| is long and very flexible, so as to allow for the extra swinging motion of the side plate 92a and also to permit the hooks 12 to slip sidewise behind a cartridge in the trough 10.

By the mechanism thus far described, a cartridge of porous carbon or similar material is soaked in liquid oxygen for one revolution of the disc 45, is thereupon advanced to its inner compartment 1|)a by itsassociated feeding arm 1|. is then raised to the dotted line position in Fig. 10 by its plate 14 and rod 15, is then advanced horizontally to axial position by its carrier 9U as shown in Fig. 11, and, after a momentary pause to overcome inertia, the ,cartridge is then released and the carrierYV is Withdrawn, leaving the cartridge in axial position as the reflector 22 returns to its rearmost or ring position, as indicated in Van escape device having stop plates M2 and M3 (Fig. 9).

-As the reiiector 22 moves upward, a rod H6 (Fig. 2) engages the escape device and moves it upward to the position shown in Fig. 2, in which position the plate ||2 permits the lowermost cap to escape and enter the tube 23 through an opening H5 in the side thereof, while the other plate |83 prevents downward movement of the remaining caps.

A firing-pin |20 is slidable in the tube 23 and is actuated by a lever |2| pivoted on an arm E22 carried by the reilector 22. The firing-pin |20 is held yieldngly in raised position by a spring |23. A rod |24 is connected to the outer end oi the lever |23 and is provided with an offset lower end 25 adapted to engage some fixed part of the magazine, such as one of the doors di, when the reflector 22 descends.

Such engagement will force the firing-pin abruptly downward, thus exploding the cap itil just above the restricted opening l 2@ at the lower end of the tube 23. The flash of the detonated cap ||0 -is directed to the top of the cartridge C through the opening l2@ and instantly det- `onates or explodes the cartridge. The restriction of the tube 23 prevents premature escape of the released cap.

The upper end of the cartridge C is preferably recessed as indicated in Fig. 2, so that less materia] will be exploded in the more confined space at the top of the reector, thus avoiding excessive pressure at this point.

While this method of firing the cartridges is commonly preferred,` an alternative method is indicated in Fig. 18, where the cartridge C' has a cap |21 permanently assembled therewith and adapted to be engaged by a tiring-pin |22 in the renector |29 as the reiiector descends. The cap |21 must obviously be protected from the liquid oxygene by coating with some non-porous materlal.

When starting the rocket, a special initial detonating cartridge may be positioned in the reflector 22 by forcing its upper end into the restricted passage |23 and this cartridge may be fired by such electrical connections as are used in blasting.

This general method of propelling rocket apparatus has many and important advantages. As the cartridges are not, closely confined when exploded, extremly high pressures are avoided and it is possible to usev detonating charges which act'substantially instantaneously and which give off gases at such extremely high speeds that they cannot be safely used in an enclosedor confined space. With the construction herein shown, theA pressures against the reflector 22 are not excessive, even with the most powerful explosives, as

.the forces are reflected rather than resisted. The

extremely rapid reflection and election of the gases also prevents excessive heating, as the gases are generated at a point substantially removed from the conical surface and are not in contact with the inner surface of the reflector .for an appreciable time.

Since the gases strike the surface of the cone at maximum speed and do not require further expansion, the use of an elongated nozzle to utilize the force of expansion is unnecessary. Furthermore, since reflection will take place at any gas velocity and with gas of any density, modification of the nozzle for different velocities and densities is also unnecessary.

Furthermore, I have found by experiment that detonating cartridges produce a greater propulsive force in the described reflecting type of nozzle than was produced in nozzles previously used in rocket apparatus where combustion took place in a confined combustion chamber. I have also found that the propulsive force is greater in a partial vacuum than at atmospheric pressure, which particularly adapts my invention to high altitude research.

For certain purposes, it may at times be desirable to lire all of' the remaining cartridges simultaneously. For this purpose a timer |30 sive head i3d fires all remaining cartridges which have been soaked by the opening of the valve |33.

Instead of using the large dumping valve |33, I may discharge the remaining liquid in the tank 32 through the regular feed pipe di by providing a spring-pressed plunger |40 (Fig. 19) adapted to be electrically released by the -timer V|30 and to thereafter hold the valve 42 continuously open. The liquid in the tank 32 is usually under some pressure.

If cartridges of a solid detonating mixture are employed, no release of liquid is required and the entire load may be fired at any time by a suitable explosive head as E33.

In the specification and claims the term ,rearward is to be understood as toward the following end of the rocket apparatus when in flight, or toward the lower end of the apparatus as viewed in Figs. 1 and 2. Y

Having thus described my invention and the advantages thereof, I do not wish to be limited to the details herein disclosed, otherwise than as set forth in the claims, but what I claim is:

l. In a rocket apparatus, a rearwardly 'open and unobstructed casing elongated in line of V flight, a rearwardly-open gas reflector mounted on said casing and concentric therewith and provided with an internal rearward reflecting surface forming substantially a 90 cone, an elongated explosive cartridge, means mounted in said casing and effective to present said cartridge in the longitudinal axis of said casing and-reflector but substantially spaced radially from the side walls thereof and having one end spaced rearward from but adjacent the forward end of said reflector, and means embodied in said apparatus effective to explode said cartridge in said axial position and in said dened relation to said casing and reflector, said`conical reflector being thereafter effective to rearwardly reflect the gases produced by the explosion of said cartridge ln said reflector along paths substantially parallel to the longitudinal axis of said casing and reflector.

2. The combination ln rocket apparatus as set forth in claim 1, in which the gas reflector has an additional parabolic internal reflecting surface at its open rear edge portion, which parabolic surface forms a continuation` of the internal tank 32 will be allowed to dow into the magazine f 33 and to soak all of the 'cartridges remaining therein. The entire charge may then be fired by anv explosive head |34 (Fig.` 1) also controlled from the timer |30, or it may be fired by impact or in any other desired manner.

In Fig. 21 I have shown a wiring diagram for the load-dumping devices above described. The timing device |30 is connected by wires W' to fusible links F and F', one of which holds the valve |33 in raised or closed position, While the other holds the plunger |3| in raised position. When a circuit is closed by the timer |30 through the wires W', the fusible linksF and F' willl be melted, whereupon the valve |33 will open and the plunger |3| will move downward to locking position.

The timer |3|) is also connected by Wires W2 to the explosive head orring device |34 and the circuit is closed by the timer through the wires W2 at a predetermined interval after the closing of the circuit through the wires W'. When the circuit is closed through the wires W2, the exploconical reflecting surface of said reflector and additionally directs the explosion gases rearward.

3. In a rocket apparatus, a easing elongated in line of flight, a, rearwardly-open gas reflector mounted therein and concentric therewith, an annular cartridge-soaking trough mounted in and concentric with said casing and holding a plurality of elongated 'cartridges parallel to the casing axis, means in said casing to supply and automatically maintain a predetermined amount of liquid oxidizing Vagent in said trough, devices in Y said casing effective to remove soaked and explo- 1 sive cartridges successfully from said trough and to present said cartridges successively in alignment with the axis of said reflector and adjacent n 4. The combination in a rocket apparatus as set forth in claim 3, in which the gas reflector is mounted for recoil and return movements in said casing, and in which the means for removing and presenting cartridges is engaged and actuated by said reflector during recoil, and in which the exploding means is engaged and actuated by said reflector as its return movement is completed.

5. In a rocket apparatus, a casing elongated in line of flight, an annular soaking trough mounted in said casing and concentric therewith and adapted to hold a plurality of elongated solid porous cartridges parallel to the casing axis, a storage chamber in said casing for a liquid oxidizing agent, means to feed said liquid agent from said chamber to said trough, and means to maintain a fixed level of said liquid in said trough for soaking said cartridges.

6. In a rocket apparatus, a casing elongated inline of flight, a rearwardly open gas reflector mounted in said casing and concentric therewith, an annular soaking trough mounted in said casing and concentric therewith and adapted to hold a plurality of elongated solid porous cartridges parallel to the casing axis, a storage chamber to supply a liquid oxidizing agent to said trough, means to remove successive soaked cartridges from said tro-ugh and to successively present said cartridges in axial position within said reflector and adjacent to but spaced from the forward end thereof and spaced from the conical side wall thereof by successive radially inward, upward and additional radially inward movements, and automatic means to explode each cartridge so positioned in said reflector, said reflector having a substantially conical reflecting surface which is effective to reflect the explosion gases rearward along paths parallel to the longitudinal axis of said casing and reflector.

7. Rocket apparatus as set forth in claim 6, in

' which means is provided to deliver direct to the unused cartridgesin said trough and casing all of the remaining liquid oxidizing agent in said storage chamber, and in which additional means is provided to thereafter explode all of the remainingcartridges simultaneously in said trough and casing. v

8. In a rocket apparatus, a casing elongated in line of flight, an annular trough in said casing containing a liquid oxidizing agent, a plurality of solid porous elongated cartridges held in said trough parallel to the casing axis and immersed in said liquid agent, a gas reiiector rotatably mounted in said casing concentric with the axis thereof and also mounted for reciprocatlon along said axis, means to explode successive cartridges in said reflector, said reector being displaced forwardly in said casing by the reaction of each explosion, yielding means in said casing to return said reflector rearward to operative position for the next explosion, means inrsaid casing to intermittently feed said reflector angularly in said casing and relative to said trough, said latter means being actuated by said reflector at each reciprocation thereof, cartridge-feeding devices mounted in said casing and associated with said about the entire periphery thereof and to present said cartridges successively in alignment with and adjacent to but spaced from the forward end 0f said reflector, and magazine means in said casing effective to replace each cartridge removed from said trough by a fresh cartridge which is thereafter removed from said trough by said cartridge-presenting means but only after said intermittent feeding means has advanced said reflector through a substantially complete revolution.

9. The combination in rocket apparatus as set forth in claim 8, which additionally comprises a plurality of separate cartridge compartments mounted in said casing inwardly adjacent said annular` trough, and in which combination said cartridge-presenting means includes means in said casing effective to move each cartridge successively to its associated inner compartments, and means in said casing effective t0 lift each cartridge successively from its inner compartment to a raised position relative thereto and in which raised position it is engageable by one of said cartridge-feeding devices for movement to axial position in said casing and reflector.

l0. In a rocketapparatus, a casing elongated in line of flight, a gas reflector movably mounted in said casing to reciprocate axially and concentrically therein, means actuated by said reflector effective to feed an elongated cartridge radially inward to axial position in said apparatus as said reflector is moved forward by explosion re- "coil, and means controlled by said reflector and effective to fire said cartridge as said reflector returns to its rearward position, said feeding means including a cartridge carrier, vmeans to hold a cartridge therein, means to move said cartridge transversely of the longitudinal axis of said casing, means to stop andfhold said carrier momentarily with its cartridge in axial position in said reflector, means to release the cartridge thus positioned, and means to withdraw said carrier as said reflector moves rearward and before said'cartridge/is fired.

11. Rocket apparatus as set forth in claim 10, in which the cartridge carrier is mounted on an extensible lazy-tongs linkage which is engaged and elongated toward 'the casing axis by said reflector in its forward recoil movement.

12. In a rocket apparatus, a casing elongated I in line of flight, a gas reflector mounted in and 

